CN106917643A - Turbine rotor blade with shield - Google Patents
Turbine rotor blade with shield Download PDFInfo
- Publication number
- CN106917643A CN106917643A CN201611235488.1A CN201611235488A CN106917643A CN 106917643 A CN106917643 A CN 106917643A CN 201611235488 A CN201611235488 A CN 201611235488A CN 106917643 A CN106917643 A CN 106917643A
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- Prior art keywords
- wing
- contact surface
- suction
- rotor blade
- pressure
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- 238000010276 construction Methods 0.000 claims description 21
- 230000010354 integration Effects 0.000 claims description 17
- 238000009434 installation Methods 0.000 claims description 8
- 230000015572 biosynthetic process Effects 0.000 claims description 7
- 230000008859 change Effects 0.000 claims description 7
- 230000000007 visual effect Effects 0.000 claims description 4
- 239000003082 abrasive agent Substances 0.000 claims description 2
- 239000000567 combustion gas Substances 0.000 claims description 2
- 238000011144 upstream manufacturing Methods 0.000 description 13
- 238000007789 sealing Methods 0.000 description 10
- 238000013461 design Methods 0.000 description 8
- 238000001816 cooling Methods 0.000 description 6
- 210000003414 extremity Anatomy 0.000 description 6
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- 239000000446 fuel Substances 0.000 description 4
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- 230000002349 favourable effect Effects 0.000 description 2
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- 230000002159 abnormal effect Effects 0.000 description 1
- 230000002547 anomalous effect Effects 0.000 description 1
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- 230000003139 buffering effect Effects 0.000 description 1
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
It is a kind of to be configured to rotor blade used in the rotor blade of row's same configuration, for gas turbine.Rotor blade may include to be limited to the airfoil between pressure face and suction plane, and in across shield.In across shield may include the pressure wing and suction the wing.In interface between the adjacent rotor blades in the pressure wing and the suction wing rotor blade that is configured to cooperatively form in the rotor blade of row's same configuration of shield.Interface may include：The pressure wing contact surface on the pressure wing is arranged on, it is relative with the suction wing contact surface being arranged on the suction wing across gap；And the predetermined migration between pressure wing contact surface and suction wing contact surface.Predetermined migration is configurable for, when expected operating condition makes gap-closing, making contact surface desirably be aligned.
Description
Technical field
The application relates generally to the design on the rotor blade in combustion engine or gas-turbine unit, manufactures and use
Equipment, method and/or system.More specifically but not via limitation, the application be related on having in across shield turbine
The equipment and component of rotor blade.
Background technology
In combustion engine or gas-turbine unit (hereinafter " gas turbine "), it is known that pressurize within the compressor
Air is used for burning fuel in the burner and generates hot burning gas stream, thus gas flow downstream through it is one or more
Turbine, so that energy can be from its extraction.According to such engine, generally, rows of circumferentially spaced rotor blade is from supporting
Rotor disk is extended radially outward.Each rotor blade typically comprises the blade in the corresponding dovetail groove allowed in rotor disk
The dovetail part of assembly and disassembly, and extended radially outward from dovetail part and mutual with working fluid stream through engine
The airfoil of effect.Airfoil has concave pressure side and convex suction side, and they are between corresponding leading edge and trailing edge along axle
To extension, and radially extended between root and end.It will be appreciated that blade end is tight with the outside static surface in footpath
Ground interval, the leakage therebetween for minimizing the burning gases of flow further downstream between turbo blade.
The shield of the end of airfoil or " end shield " are implemented generally in rear class or rotor blade, to provide end
The contact point at place, manages wheel blade vibration frequency, realizes buffering source, and reduces the leakage on the end of working fluid.After given
The length of the rotor blade in level, the cushioning effect of end shield provides significant benefit for durability.However, it is contemplated that
To end shield add to component weight and other design standards (including tolerance exposed to high temperature and extreme mechanical load it is thousands of
The operation of hour), it is difficult completely using benefit.Therefore, although big end shield having due to their sealing gas paths
Efficacious prescriptions formula and their being stably connected with of being formed between adjacent rotor blades and be desirable, it will be appreciated that this
Class shield due on rotor blade, the drawing load of the increase particularly at the base portion of airfoil and be troublesome because its is necessary
The whole load of supporting blade.
A kind of mode for solving everything be shield is positioned on airfoil it is relatively low.I other words, substitute shield
Added to the end of airfoil, shield is centrally positioned near radial zone.As used in this article, such shield is referred to as "
In across shield ".At relatively low (that is, the inside) radius, the quality of shield causes the low-level stress of drop to rotor blade.So
And, some problem of the design and use on conventional midspan shrouds is recognized by the present inventor.These problems be generally related to for
Structure and further advantage and as the contact wear of the device for being mechanically engaged adjacent aerofoil part between shield in being included in
Surface or the performance of pad.Even if when sane, these contact surfaces are rapidly worn and torn, and provide the trend of misalignment.Such misalignment is led
Cause tension force and shearing force to put on contact surface, this be attached to because contact surface is typically in across the surface of shield non-collection
Into pad and cause the deleterious wear that component can be made rapidly to degenerate.Additional problem such as aerodynamic losses can also be lost by this class
Standard causes.Finally, the weight in such shield can reduce while still meeting in the degree of construction standard, the life-span of rotor blade can
Extension.
As it will be realized, according to these and other standard, the design of the rotor blade with shield includes many complexity
The generally consideration of competition.These are balanced in the way of to optimize or improve one or more desired performance standards to consider while still
Suitably promote the novel designs of long-lived structure steadiness, part life, manufacturability and/or cost-effective power operation
Represent the technology of economic worth.
The content of the invention
Therefore, This application describes it is a kind of be configured to it is being used in the rotor blade of row's same configuration, for firing
The rotor blade of air turbine.Rotor blade may include：It is limited between shaped pressure face and laterally relative convex suction plane
Airfoil；And in across shield.In may include the pressure wing that extends from the pressure face of airfoil and from airfoil across shield
The suction wing that suction plane extends.In across shield the pressure wing and suction the wing be configured to cooperatively form row's same configuration
Rotor blade in rotor blade in adjacent rotor blades between interface.Interface may include：It is arranged on the pressure wing
Pressure wing contact surface, it is relative with the suction wing contact surface being arranged on the suction wing across gap；And pressure wing contact surface with
Predetermined migration between suction wing contact surface.Predetermined migration is configurable for, when expected operating condition makes gap-closing, making to connect
Contacting surface is desirably aligned.
A kind of rotor blade for gas turbine of technical scheme 1., the rotor blade configuration be used for attach to turn
Sub-disk and used in the rotor blade of the circumferentially spaced row's same configuration of rotor disk, the rotor blade is also wrapped
Include：
Airfoil, it is limited between shaped pressure face and laterally relative convex suction plane, wherein the pressure face and institute
State suction plane to be axially extended between relative leading edge and trailing edge, and radially prolong between outside end and medial extremity
Stretch, the medial extremity attaches to the root for being configured to that the rotor blade is attached to the rotor disk；And
In across shield, it includes the pressure wing extended from the pressure face of the airfoil and the suction from the airfoil
Enter the suction wing of face extension；
The pressure wing and the suction wing in wherein described across shield are configured so as to cooperatively form a row identical
Interface between the adjacent rotor blades of the installation in the rotor blade in the rotor blade of construction；
Wherein described interface includes：
The pressure wing contact surface on the pressure wing is arranged on, it connects across gap with the suction wing being arranged on the suction wing
Contacting surface is relative；And
Predetermined migration between the pressure wing contact surface and the suction wing contact surface, the predetermined migration is configured to pre-
When phase operating condition makes the gap-closing so that producing contact therebetween, make the pressure wing contact surface relative to the suction
Wing contact surface is desirably aligned.
Rotor blade of the technical scheme 2. according to technical scheme 1, it is characterised in that the airfoil includes reversing
Construction, wherein the airfoil configuration is radially extended into the airfoil between the medial extremity and the outside end
When, with the torsion around longitudinal axis, its solution is turned round and causes the pressure wing contact surface and the suction wing at the interface to contact
Relative movement between face；
Wherein described expected operating condition includes causing the torsion formation of the airfoil fully to solve torsion to make the gap
The operating condition of closure；And
Wherein described expected operating condition includes the desired speed of the rotor blade in the turbine.
Rotor blade of the technical scheme 3. according to technical scheme 2, it is characterised in that it is right that the desired speed includes
The rotating speed of the operation at the 90% of the nominal load of gas turbine described in Ying Yu or higher than 90%；
The torsion formation of wherein described airfoil is configured so as to little by little change between the medial extremity and outside end
Become the alternate angle for the airfoil；And
Include across shield the shield in the position range that is arranged on the airfoil in wherein described, the position range is limited
It is outer at inboard boundary and the 85% of the radial height of the airfoil at the 25% of the radial height of the airfoil
Between lateral boundaries.
Rotor blade of the technical scheme 4. according to technical scheme 1, it is characterised in that the gas turbine includes limit
Determine the working-fluid flow path through the compressor being positioned at front end and the turbine for being positioned at rear end, its orientation limits institute
State the front direction and rear direction in gas turbine；
Wherein flow direction includes working fluid through the expected flow direction in the working-fluid flow path, the flowing side
To the central axis for being defined as parallel in the compressor and the turbine gas turbine, and along the rear direction
Orientation；And
Wherein direction of rotation includes the expected direction of rotation for the rotor blade during the operation of the gas turbine.
Rotor blade of the technical scheme 5. according to technical scheme 4, it is characterised in that the rotor blade includes structure
Make the rotor blade for being used in the turbine；
Wherein described interface is formed between the section for circumferentially overlapping of the pressure wing and the suction wing；And
Wherein：
The pressure wing includes front and back, described above to face the front end of the gas turbine, and it is described behind
Face the rear end of the gas turbine；And
The suction wing includes front and back, described above to face the front end of the gas turbine, and it is described behind
Face the rear end of the gas turbine.
Rotor blade of the technical scheme 6. according to technical scheme 5, it is characterised in that in the pressure wing and described
Suck in the section for circumferentially overlapping of the wing, the pressure wing is positioned at the suction wing front so that：
The pressure wing contact surface be formed in the pressure wing it is described below on；And
It is described suction wing contact surface be formed in it is described suction the wing it is described above on.
Rotor blade of the technical scheme 7. according to technical scheme 6, it is characterised in that：
The pad of the pressure wing contact surface including non-integration, its be attached to the pressure wing it is described behind flat section and from
Its protrusion；And
The suction wing contact surface includes the pad of non-integration, its be attached to the suction wing it is described before flat section and from
Its protrusion.
Gas turbine of the technical scheme 8. according to technical scheme 7, it is characterised in that：
The pressure wing it is described behind the pad of the non-integration include the thickness of constant so that be attached to the pressure
The power wing it is described behind the flat section when, the pressure wing contact surface is flat；
The suction wing it is described before the pad of the non-integration include the thickness of constant so that be attached to the suction
Enter the wing it is described before the flat section when, the suction wing contact surface is flat；And
Each in the pad of wherein described non-integration includes high-abrasive material.
Gas turbine of the technical scheme 9. according to technical scheme 7, it is characterised in that lateral profile is included such as from outer
The profile at the interface of radial direction visual angle viewing；And
Wherein press the lateral profile：
On with a distance from the airfoil, the pressure wing contact surface includes distal edge and proximal edge；And
On with a distance from the airfoil, the suction wing contact surface includes distal edge and proximal edge.
Gas turbine of the technical scheme 10. according to technical scheme 9, it is characterised in that by the lateral profile, institute
Stating pressure wing contact surface and the suction wing contact surface includes the oblique structure on the flow direction；And
Wherein：
The oblique structure of the pressure wing contact surface is included in the pressure wing contact surface and extends to institute from the distal edge
Towards the inclination of the direction of rotation of the rotor blade when stating proximal edge；And
The oblique structure of the suction wing contact surface is included in the suction wing contact surface and extends to institute from the proximal edge
Towards the inclination of the direction of rotation of the rotor blade when stating distal edge.
Gas turbine of the technical scheme 11. according to technical scheme 10, it is characterised in that by the lateral profile：
First jiao be formed slopely between the pressure wing contact surface and the flow direction of the pressure wing contact surface,
Described first jiao is included between 10 to 80 degree；
Second jiao be formed slopely between the suction wing contact surface and the flow direction of the suction wing contact surface,
Described second jiao is included between 10 to 80 degree；And
The predetermined migration at the interface includes circumferential offset.
Gas turbine of the technical scheme 12. according to technical scheme 11, it is characterised in that on the direction of rotation,
The circumferential offset includes：
The distal edge of the suction wing contact surface is connect described in the pressure wing contact surface before being rotated with the circumferential offset
Proximal edge；And
The proximal edge of the suction wing contact surface is connect described in the pressure wing contact surface before being rotated with the circumferential offset
Distal edge.
Gas turbine of the technical scheme 13. according to technical scheme 12, it is characterised in that described in the interface
The relative movement between pressure wing contact surface and the suction wing contact surface includes estimated circumferential deflection；
Wherein described circumferential offset is configured to correspond to the estimated circumferential deflection so that：
It is described suction wing contact surface the distal edge when the expected operating condition makes the gap-closing, with the pressure
The proximal edge of wing contact surface is circumferentially aligned；And
It is described suction wing contact surface the proximal edge when the expected operating condition makes the gap-closing, with the pressure
The distal edge of wing contact surface is circumferentially aligned.
Gas turbine of the technical scheme 14. according to technical scheme 12, it is characterised in that the interface it is described pre-
Fixed skew includes radial deflection；And
Wherein described radial deflection includes that the pressure wing contact surface offsets along lateral direction from the suction wing contact surface.
Gas turbine of the technical scheme 15. according to technical scheme 14, it is characterised in that the radial deflection includes：
The outer ledge of the pressure wing contact surface is positioned by the radial deflection of the outer ledge of the suction wing contact surface
In outside；And
The inside edge of the pressure wing contact surface is positioned by the radial deflection of the inside edge of the suction wing contact surface
In outside；
The relative movement between the pressure wing contact surface and the suction wing contact surface in wherein described interface includes
Estimated radial deflection；And
Wherein described radial deflection is configured to correspond to the estimated radial deflection so that：
The outer ledge of the pressure wing contact surface when the expected operating condition makes the gap-closing, with the suction
The outer ledge for entering wing contact surface is radially aligned；And
The inside edge of the pressure wing contact surface when the expected operating condition makes the gap-closing, with the suction
The inside edge for entering wing contact surface is radially aligned.
Gas turbine of the technical scheme 16. according to technical scheme 12, it is characterised in that the interface it is described pre-
Fixed skew includes angular variation, and the angular variation includes that described first jiao of the pressure wing contact surface sucks wing contact surface with described
Described second jiao between difference.
Gas turbine of the technical scheme 17. according to technical scheme 16, it is characterised in that described in the interface
The relative movement between pressure wing contact surface and the suction wing contact surface includes estimated angular deflection；And
Wherein described angular variation is configured to correspond to the estimated angular deflection so that the pressure wing contact surface is in the expected behaviour
When making the gap-closing as condition, angulately it is aligned with the suction wing contact surface.
Technical scheme 18. is a kind of to have the gas turbine of row's rotor blade, and the row rotor blade attaches to rotor
Disk and circumferentially spaced around rotor disk, wherein each in the rotor blade in the row rotor blade includes：
Airfoil, it is limited between pressure face and laterally relative suction plane；And
In across shield, it includes the pressure wing extended from the pressure face of the airfoil and the suction from the airfoil
Enter the suction wing of face extension；
The pressure wing and the suction wing in wherein described across shield are configured so as to cooperatively form the row rotor
Interface between the adjacent rotor blades of the installation in the rotor blade in blade；And
Wherein described interface includes：
The pressure wing contact surface on the pressure wing is arranged on, it connects across gap with the suction wing being arranged on the suction wing
Contacting surface is relative；And
Predetermined migration between the pressure wing contact surface and the suction wing contact surface, the predetermined migration is configured to pre-
When phase operating condition makes the gap-closing so that producing contact therebetween, make the pressure wing contact surface relative to the suction
Wing contact surface is desirably aligned.
Gas turbine of the technical scheme 19. according to technical scheme 18, it is characterised in that lateral profile include such as from
The profile at the interface of outer radial visual angle viewing；And
Wherein press the lateral profile：
On with a distance from the airfoil, the pressure wing contact surface includes distal edge and proximal edge；And
On with a distance from the airfoil, the suction wing contact surface includes distal edge and proximal edge；
The predetermined migration at wherein described interface includes circumferential offset；And
Wherein on the direction of rotation, the circumferential offset includes：
The distal edge of the suction wing contact surface is connect described in the pressure wing contact surface before being rotated with the circumferential offset
Proximal edge；And
The proximal edge of the suction wing contact surface is connect described in the pressure wing contact surface before being rotated with the circumferential offset
Distal edge.
Gas turbine of the technical scheme 20. according to technical scheme 19, it is characterised in that the interface it is described pre-
Fixed skew includes radial deflection；And
Wherein described radial deflection includes that the pressure wing contact surface offsets along lateral direction from the suction wing contact surface.
These and other feature of the application will check retouching in detailed below for preferred embodiment when being carried out with reference to accompanying drawing
Become apparent when stating with appended claims.
Brief description of the drawings
By carefully studying the description in more detail below of the exemplary embodiment of the invention carried out together with accompanying drawing, will more
These and other features of the invention are fully understood by and recognize, in the figure：
Fig. 1 is the schematic diagram of the exemplary gas turbine that may include turbo blade according to present aspects and embodiment；
Fig. 2 is the section view of the compressor section of the gas turbine of Fig. 1；
Fig. 3 is the section view of the turbine of the gas turbine of Fig. 1；
Fig. 4 is the exemplary turbine rotor arranged including internal cooling configuration and structure according to present aspects and embodiment
The side view of blade；
Fig. 5 is the section view along the sight line 5-5 of Fig. 4；
Fig. 6 is the section view along the sight line 6-6 of Fig. 4；
Fig. 7 is the section view along the sight line 7-7 of Fig. 4；
Fig. 8 is the exemplary turbine rotor blade that may include end shield and construction according to present aspects and embodiment
Perspective view；
Fig. 9 be according to aspect of the invention or the present invention can be used in it have in across shield exemplary rotor blade
Perspective view；
Figure 10 be according to aspect of the invention or the present invention can be used in it have in across shield rotor blade example
The perspective view of property mounting arrangements；
Figure 11 be according to aspect of the invention or the present invention can be used in it have in across shield rotor blade example
The outside figure of property mounting arrangements；
Figure 12 be according in the having of aspect of the invention across shield airfoil perspective view；
Figure 13 be according to embodiments of the invention with formed in interface across shield rotor blade exemplary installation cloth
The perspective view put；
Figure 14 be according to embodiments of the invention with formed in interface across shield rotor blade exemplary installation cloth
The lateral profile view put；
Figure 15 be according to embodiments of the invention with formed in interface across shield rotor blade exemplary installation cloth
The view downstream seen put；
Figure 16 be according to embodiments of the invention with formed in interface across shield rotor blade exemplary installation cloth
The view upstream seen put；And
Figure 17 be according to embodiments of the invention with formed in interface across shield rotor blade exemplary installation cloth
The view downstream seen put.
Specific embodiment
Present aspects and advantage illustrate in the following description below, or can be from being described as it will be evident that or can
By learning by doing of the invention.The present embodiment of the invention is reference will now be made in detail to now, and its one or more example is in accompanying drawing
In show.Detailed description has used number designation to represent the feature in accompanying drawing.The accompanying drawing label similar or similar with description
Can be used to represent the similar or similar part of embodiments of the invention.As it will be realized, each example is via this hair of explaination
Bright offer, without the limitation present invention.In fact, be evident that to those skilled in the art, can be in the present invention
Remodeling and modification are made, without deviating from its scope or spirit.For example, the feature for being illustrated or described as the part of one embodiment can
For in another embodiment producing another embodiment.It is intended that the present invention covering be included into appended claims and they
Equivalent in the range of such remodeling and modification.It will be appreciated that scope referred to herein and the limit include being located at rule
Determine all subranges (including limit their own) in the limit, unless otherwise stated.Additionally, some terms are chosen to description originally
Invention and its component subsystem and part.In possible degree, these terms are selected based on term common in technical field
Select.Further, it will be appreciated that such term is commonly subjected to different annotations.For example, single structure can be referred to herein as
The things of part can be referred to as being made up of multiple firmwares elsewhere, or, can be referred to herein as including that the things of multiple components can be
Other places are referred to as single component.When the scope of the present invention is understood, the particular term for using should be not only noted, and note appended
Description and context, and quote and the structure of component of description, construction, function and/or use, including term is related to some figures
Mode and certain appended claims in the accurate of term use.Although additionally, following instance is on certain form of
Gas turbine or turbogenerator are proposed, but the technology of the application could be applicable to the propeller for turboprop of (and being not limited to) other species
What the technical staff in machine, such as correlative technology field will be understood that.It is understood, therefore, that unless otherwise stated, otherwise using
Language " gas turbine " use herein is intended to broadly, and applicability of the invention is limited into various types of turbine hairs
Motivation.
The property how given gas turbine operates, some terms are proved when describing in terms of some of their function
It is particularly useful.These terms are defined as follows with them, unless explicitly stated.
Term " preceding " and " rear " they refer to the direction of the orientation on gas turbine, and more specifically, the pressure of engine
The relative positioning of contracting machine section and turbine.Therefore, as used in this article, term " preceding " refers to compressor end, and " rear "
It refer to turbine end.It will be appreciated that, each in these terms may be used to indicate along the mobile side of the central axis of engine
To or relative position.
Term " downstream " and " upstream " be used to indicating herein on move through its flowing direction (hereinafter
Be " flow direction ") specified conduit or flow path in position.Therefore, term " downstream " refers to flow of fluid through specifying
The direction of conduit, and " upstream " refers to direction in contrast.On it will be understood by the skilled person that content, these use
Language may be interpreted as in given normal or estimated operation through the flow direction of conduit.As it will be realized, in gas turbine
In compressor and turbine, working fluid is directed across the working-fluid flow path of annular shape and is accommodated within,
The working-fluid flow path of the annular shape limits around the central axis of engine.In such cases, term " flowing side
To " can represent represent through the working-fluid flow path of engine working fluid Utopian expected flow direction base
Quasi- direction.The reference direction can be regarded as the central axis parallel to gas turbine and the side oriented along downstream or rear direction
To.
Thus, for example, the working fluid stream through the working-fluid flow path of gas turbine can be described as starting being edge
The air that expected flow direction is pressurizeed through compressor, the burning gases in the combust time-varying of fuel one for burner, and
And finally when it passes through turbine along expected flow direction expansion.Alternately, working fluid stream can be described as towards gas turbine
Front end or upstream end start in preceding or upstream position, generally moved along downstream or rear direction, and last towards combustion gas whirlpool
The rear or downstream of wheel terminates at rear or downstream position.
When many components (e.g., compressor and turbine rotor blade) of gas turbine rotate during operation, term rotation
Turn front and rear swivel can be used to describe sub- component or the positioning of subregion on in-engine rotation.Therefore, such as will
Recognize, direction (hereinafter " direction of rotation ") demarcation of location of the rotation in these term pressable contracting machines or turbine.Give
Determine the normal or estimated operation of gas turbine, direction of rotation can be regarded as the expected direction of rotation for component.
Additionally, the construction of given gas turbine, particularly around the compressor and turbine of common axle or rotor
Arrangement, and the total cylindrical configurations of many burner types, the term for describing the position on axis can herein have rule
Then use.In this aspect, it will be appreciated that term " radial direction " refers to movement or the position perpendicular to axis.It is related to this,
Description can be needed from the relative distance of central axis.In such cases, if for example, first component is resident into than second component
Closer to central axis, then first component will be described as " radially inner side " or " inner side " in second component.On the other hand, such as
Fruit first component is resident into further from central axis, then first component will be described as " radial outside " or " outer in second component
Side ".As used in this article, term " axial direction " refers to movement or the position parallel to axis, and term " circumferential " refer to
Movement or position around axis.Unless otherwise stated or based on context it is clear that otherwise describing the position on axis
These terms should be construed to the central axis of compressor and turbine on engine, as by extending through each
What rotor was limited.However, term can also be used on the longitudinal axis of the component of some in gas turbine or subsystem, such as example,
The longitudinal axis that common cylindrical shaped or " tubular " burner are typically positioned around.
Finally, term " rotor blade " represents the pivoting leaf of compressor or turbine in the case of without other particularity
Piece, and therefore may include both compressor rotor blade and turbine rotor blade.Term " stator vane " is without other spy
Refer to the static blade of compressor or turbine in the case of different property, and therefore may include compressor stator blade and turbine stator
Both blades.Term " blade " can be used to be generally designated by any type of blade.Therefore, in the situation without other particularity
Under, term " blade " include all types of turbine engine blades, including compressor rotor blade, compressor stator blade,
Turbine rotor blade, turbine stator vane etc..
Via background, referring now particularly to accompanying drawing, Fig. 1 to 3 shows and can be used in it according to the present invention or the present invention
Exemplary gas turbine.It will be appreciated by those skilled in the art that the present invention can be not limited to the use of the type.As stated
, the present invention can be used for gas turbine, such as be used to generate electricity and the engine in aircraft, steam turbine engines and other types
Rotary engine in, as the skilled person will recognize.Therefore it provides example be not intended to limitation, unless in addition
Statement.Fig. 1 is the schematic diagram of gas turbine 10.Generally, the burning that gas turbine passes through the fuel from by compressed air stream
The pressurization thermal current extracting energy of generation and operate.As shown in fig. 1, gas turbine 10 may be configured with axial compressor 11 and combustion
Burner 13, axial compressor 11 is mechanically coupled to the turbine or turbine 12 in downstream, burner 13 by common axis or rotor
It is positioned between compressor 11 and turbine 12.As shown in fig. 1, gas turbine can be formed around central axis common 19.
Fig. 2 shows the view of the exemplary multi-stage axial compressor 11 in the gas turbine that can be used for Fig. 1.As indicated,
Compressor 11 can have multiple levels, and wherein each includes a bank of compressors rotor blade 14, and a bank of compressors stator vane
15.Therefore, the first order may include the bank of compressors rotor blade 14 around central shaft rotation, be followed by keeping quiet during operation
A bank of compressors stator vane 15 only.Fig. 3 shows exemplary turbine section or turbine in the gas turbine that can be used for Fig. 1
12 partial view.Turbine 12 may also comprise multiple levels.Three exemplary stages are shown, but more or less level there may be.
Each grade may include multiple turbine nozzles or stator vane 17 of remains stationary during operation, be followed by during operation around axle
Multiple turbine vanes or rotor blade 16 of rotation.Turbine stator vane 17 generally circumferentially be spaced, and around
Rotation axis is fixed on shell.Turbine rotor blade 16 can be arranged on turbine wheel or rotor disk (not shown) to be used for around center
Axis rotates.It will be appreciated that, turbine stator vane 17 and turbine rotor blade 16 are located across the hot gas road of turbine 12
In footpath or working-fluid flow path.The flow direction of burning gases or working fluid in working-fluid flow path is by arrow
Indicate.
In an example of the operation for gas turbine 10, compressor rotor blade 14 is in axial compressor 11
Rotation compressible air stream.In burner 13, when compressed air mixes and lights with fuel, releasable energy.Come from
The hot gas of the gained of burner 13 or the stream of working fluid are then guided on turbine rotor blade 16, and this causes turbine to turn
Blades 16 rotate around axle.In this manner, the energy of working fluid stream is converted into rotating vane and rotary shaft (to rotor leaf
Connection between piece and axle) mechanical energy.The mechanical energy of axle then can be used to drive the rotation of compressor rotor blade 14 so that
The necessary supply of compressed air is produced, and for example also makes electrical power generators.
For the purpose of background, Fig. 4 to 7 is provided according to aspects of the present invention or aspect of the invention can practice in it
Turbine rotor blade 16 view.As it will be realized, these figures provide into the total construction for showing rotor blade, to chat
Stating the spatial relationship between component and the region in these blades is used for referring next to while it is internal and outer to also describe influence
The geometrical constraint and other standards of portion's design.Although the blade of the example is rotor blade, it will be appreciated that unless in addition
Statement, otherwise it is can also be applied to other types of blade in gas turbine.
As indicated, rotor blade 16 may include the root 21 for attaching to rotor disk.For example, root 21 may include construction
For the dovetail part 22 in the corresponding dovetail groove in the periphery of rotor disk.Root 21 may also include handle 23, and it is in dovetail
Extend between portion 22 and platform 24.As indicated, platform 24 forms the junction surface of root 21 and airfoil 25, it is to block through whirlpool
Effective component of the working fluid stream for taking turns 12 and the rotor blade 16 for causing rotation.Platform 24 can limit the inner side of airfoil 25
End, and the inboard boundary through the working-fluid flow path of turbine 12 section.
The airfoil 25 of rotor blade may include shaped pressure face 26 and circumferentially or laterally opposed convex suction plane 27.
Pressure face 26 and suction plane 27 can be axially extended between relative leading edge 28 and trailing edge 29 respectively.Pressure face 26 and suction plane
27 can also extend in a radial direction from medial extremity (that is, platform 24) to the outside end 31 of airfoil 25.Airfoil 25 may include
Between platform 24 and outside end 31 extend bending or determine contour shape.As shown in Figures 4 and 5, the shape of airfoil 25
Can be little by little tapered when it extends between platform 24 and outside end 31.It is tapered to may include to make as shown in Figure 4
The axial direction that the distance between the leading edge 28 of airfoil 25 and trailing edge 29 reduce is tapered, and reduces as shown in Figure 5 as limited
The circumference of the thickness of the airfoil 25 being scheduled between suction plane 26 and pressure face 27 is tapered.As shown in figs 6 and 7, airfoil
25 determine contour shape may additionally include its from platform 24 extend when around airfoil 25 longitudinal axis torsion.Reverse typically
It is configured so as to gradually change the alternate angle for airfoil 25 between medial extremity and outside end 31.
For the purpose of description, as shown in Figure 4, the airfoil 25 of rotor blade 16 further may be described as including limiting to axial direction
The leading edge section or half portion and trailing edge section or half portion of each side of center line 32.Used according to herein its, axial centerline 32
Can be formed by the midpoint 34 of the camber line 35 of the airfoil 25 between connecting platform 24 and outside end 31.Additionally, airfoil
25 two sections for radially stacking that can be described as including the footpath for being limited to airfoil 25 33 inner side and outer side to the midline.Cause
This, as used in this article, the inner side section or half portion of airfoil 25 extend between platform 24 and footpath to the midline 33, and outside
Section or half portion extend between 33 and outside end 31 to the midline in footpath.Finally, airfoil 25 can be described as including pressure face area
Section half portion and suction plane section or half portion, they are as it will be realized, limit to each side of the camber line 35 of airfoil 25 and aerofoil profile
The corresponding surface 26,27 of part 25.
Rotor blade 16 may also include the internal cooling construction 36 with one or more cooling ducts 37, and cooling agent exists
One or more cooling ducts 37 are circulated through during operation.Cooling duct 37 can be from forming through the root of rotor blade 16
21 connecting portion to source of supply is extended radially outward.Cooling duct 37 can be linear, bending or combinations thereof, and
And one or more outlets or surface port are may include, by it, cooling agent is discharged and to workflow from rotor blade 16
In body flow path.
Fig. 8 is provided includes the perspective view of the exemplary turbine rotor blade 16 of end shield 41.As indicated, end shield
Near 41 outboard ends that can be positioned on airfoil 25 or place.End shield 41 may include axially and circumferentially extending flat board or
Plane institution movement, it is supported towards its center by airfoil 25.For the purpose of description, end shield 41 may include inner surface 45, outer
Side surface 44 and edge 46.As indicated, inner surface 45 is relative with outer surface 44 across the narrow radial thickness of end shield 41,
And inner surface 45 is connected to outer surface 44 by edge 46, and as used in this article, the periphery of end shield 41 is limited
Profile or shape.
Sealing track 42 can be positioned along the outer surface 44 of end shield 41.Generally, as indicated, sealing track 42 is wing
Sheet is raised, and it is extended radially outward from the outer surface 44 of end shield 41.Sealing track 42 can be along rotor blade 16
The direction of rotation or " direction of rotation " between the opposite end of end shield 41 circumferentially.As it will be realized, sealing rail
Road 42 can be used to prevent the leakage through the working fluid of radial clearance, and the radial clearance is present in end shield 41 and is worn with restriction
Between the static component of the wrapping for crossing the outer boundaries in the working-fluid flow path of turbine.In some conventional designs, sealing
Track 42 can be extended radially into the abradable static honeycomb fashion shield corresponding thereto of the gap.Sealing track 42 can
It is extended across the substantially whole circumferential lengths of the outer surface 44 of end shield 41.As used in this article, end shield 41
Circumferential lengths are the length along the end shield 41 of direction of rotation 50.Cutter tooth 43 may be provided on sealing track 42.As will be appreciated
Arrive, cutter tooth 43 can provide in the abradable coating or honeycomb of the static shield slightly wider than sealing the width of track 42
Cut-in groove.End shield 41 may include fillet region, its divergence surface for being configured to provide end shield 41 and airfoil 25
Between smooth surface transition, and end shield 41 and sealing track 42 between those smooth surface transition.
Fig. 9 to 11 provides example that can be in it in the having of practice across shield according to aspect of the invention or of the invention
The view of property turbine rotor blade.Fig. 9 be shown in which airfoil 25 include it is exemplary in across shield 75 rotor blade 16
Perspective view.As it will be realized, in have some features and property across shield 75 and the component of end shield 41 just discussed.Example
Such as, similar to end shield 41, in across shield 75 may be configured to a row install rotor blade 16 in adjacent aerofoil part 25
Between cross over.But as it will be realized, be different from end shield 41, in across shield 75 be not positioned at airfoil 25 outside end
Hold at 31 or near.Alternatively, as indicated, in zone line across shield 75 radially with airfoil 25 overlap.Therefore, in
The footpath of airfoil 25 is can be positioned on across shield 75 to the midline near 33.According to it is used herein another definition, in across shield
75 inner sides of outside end 41 that can be broadly defined to be positioned at airfoil 25 and the shield in the outside of platform 24.According to making herein
Another definition, in can also be defined to the shield that is arranged in the radial extension of airfoil 25 across shield 75.Therefore, according to
Some embodiments, the radial extension can be defined to the inboard boundary and airfoil of approximate 25% of the radial height in airfoil 25
Between the outer boundaries of approximate the 85% of 25 radial height.According to other more specifically embodiments, in across shield 75 position model
Enclose be defined to radial height in airfoil 25 approximate 33% inboard boundary approximate with the radial height of airfoil 25 66%
Outer boundaries between.
According to this construction, in may include that the wing extended from the sidepiece of airfoil 25 is raised across shield 75.These wings are convex
In each can be mentioned from the face 26,27 of its airfoil 25 for extending according to projection.Therefore, for description mesh herein
, in be referred to as including the pressure wing 76 stretched out from the pressure face 26 of airfoil 25 across span 75, and from the suction of airfoil 25
The suction wing 77 that face 27 is stretched out.As indicated, the wing 76, each in 77 can be configured to the component for stretching out vertically and circumferentially, its
Compared to airfoil 25 radial height in radial dimension relatively thin, thus make them similar to " wing ".But as " wing "
The title is not intended to be limited in the way of not stating herein.Following article will be described in more detail, in across shield 75 the wing 76, in 77
Each may be configured to be positioned at its side and in identical blade row, the wing of the adjacent rotor blades of similar constructions
Relative one in 76,77 functionally cooperates.Function cooperation may include to mechanically engage and produce the sky for improving component
Both constructions of aerodynamic performance.
Figure 10 provide have in across shield 75 rotor blade 16 when they may be arranged in Exemplary mount strap part
Perspective view, and Figure 11 provide same components top view.As indicated, in be configured to be coupled or engage across shield 75
It is adjacent in other of their rotor blade 16 across shield 75.Therefore, in rows of rotor blade 16, as indicated, from
The pressure wing 76 that the pressure face 26 of one rotor blade 16 extends may be configured to be cooperated with the suction wing 77, and the suction wing 77 is from residing at the
The suction plane 27 of the second rotor blade 16 of the side of one rotor blade 16 extends.Similarly, from the suction of the first rotor blade 16
The suction wing 77 for entering the extension of face 27 may be configured to be cooperated with the pressure wing 76, and the pressure wing 76 is from residing at the another of the first rotor blade 16
The pressure face 26 of the third trochanter blade 16 of side extends.In this manner, in can be used to produce phase during operation across shield 75
Contact point between the airfoil 25 of adjacent rotor blade 16.The contact point may alternatively appear in across shield and shield interface (hereinafter
It is " interface 85 ") between, across it, pressure wing contact surface 86 and suction wing contact surface 87 are engageable each other.Between the contact can be
It is disconnected or constant, and may depend on the operator scheme of gas turbine.As it will be realized, being coupled rotor blade 16 in like fashion
Airfoil 25 can complete to increase component natural frequency and buffer operation vibration, this can reduce the totality on rotor blade 16
Mechanical stress and increase the service life.
Referring now particularly to Figure 12 to 15, it is proposed that in having across shield rotor blade 16 some constructions, its basis
Certain aspects of the invention and exemplary embodiment.As it will be realized, these examples with reference to and in view of carried herein
The component of confession and it is related conceive, those that discuss especially with regard to aforementioned figures are described.As before, in be may include across shield 75
The suction wing 77 that the pressure wing 76 extended from the pressure face 26 of airfoil 25 and the suction plane 27 from airfoil 25 extend.In across shield
The pressure wing 76 and the suction wing 77 of cover 75 are configured to the landform that cooperated once such blade is mounted side by side on rotor disk
Into the interface 85 between the adjacent rotor blades of same design.As it will be realized, interface 85 may include to be arranged on the pressure wing 76
On pressure wing contact surface 86, and be arranged on suction the wing 77 on suction wing contact surface 87.Interface 85 may include across gap
88 contact surfaces 86,87 relative to each other.Once installing rotor blade, then the gap 88 at interface 85 can change distance.I other words, such as
Shown in Figure 14, gap 88 can be wider in cold construction or cold state, and this is not when engine is operated.In other conditions, example
Such as, when engine is operated with an ability (that is, Warm status), as shown in Figure 11, gap 88 can substantially close, so that contact surface
86,87 together.
According to the present invention, in cold state, gap 88 can for wide, and interface 85 contact surface 86, the phase between 87
Predetermined migration may include to alignment and position.Such as provided herein, the predetermined migration is configured so to make in operating condition
When gap 88 closes, contact surface 86 is realized, the alignment that caters to the need between 87.I other words, interface 85 include contact surface 86,87 it
Between predetermined migration, it is configured to, when expected operating condition causes to close gap 88, make pressure wing contact surface 86 relative
Desirably it is aligned in suction wing contact surface 87.
As discussed on Fig. 4 to 7, the airfoil of rotor blade is generally configured with torsion formation.Torsion formation typical case
Ground completes gradually to change the alternate angle of airfoil come the radial height on blade.Therefore, airfoil 25 platform 24 with it is outer
When being radially extended between side end 31, the torsion occurs around the longitudinal axis of airfoil 25, as painted in Fig. 6 and 7.Normal
During operation, the rotating speed of rotor blade can cause airfoil 25 slightly " solution is turned round ", and this can reduce the gap 88 at interface 85,
Until contact surface 86,87 together.Once being contacted, then produce in supporting across shroud ring, this can valuably reduce vibration, change
Enter durability, and resist any further solution to turn round.As it will be realized, the solution of airfoil 25 is turned round between can causing except causing to make
Other types of relative movement outside the axial movement of the closure of gap 88, between contact surface 86,87.I other words, solve the wing turned round
Type part 25 can on each other, contact surface 86,87 circumferentially, radially and/or angulately deflects across interface 85.Cause such inclined
Turn and the expected operating condition of relative movement can be defined to make the fully solution of airfoil 25 turn round to make gap 88 close required behaviour
Make.For example, it is contemplated that operating condition may include the in-engine desired speed for causing necessary solution to be turned round.According to some embodiments, in advance
Phase operating condition can be defined to the desired speed and operation temperature of engine.For example, it is contemplated that operating condition may correspond to be equal to or
The operator scheme of the gas turbine more than the 90% of the nominal load of engine.
For the purpose of description, gas turbine includes limiting through the compressor being positioned at front end and is positioned at rear end
The working-fluid flow path of turbine.As it will be realized, the orientation can be used to limit in gas turbine and its component section
Front direction and rear direction.Additionally, given normal operating, as used in this article, term " flow direction " (is such as referred to by arrow 89
Show) refer to general direction through the working fluid stream in working-fluid flow path.Therefore, in compressor and turbine,
Term flow direction can be regarded as Utopian reference direction, its central axis for being defined as parallel to gas turbine and along rear
Direction orients.As mentioned, term " direction of rotation " (such as being indicated by arrow 90) refers to the compressor or turbine section in engine
The expected direction of rotation for rotor blade during normal operating condition in section.Finally, unless otherwise stated, otherwise will reason
Solution, the present invention can be used together with the rotor blade for being configured to be used in the compressor or turbine of gas turbine.
As indicated, a preferred embodiment includes being used together with the rotor blade of the turbine for being specifically constructed for engine.
It is given defined above, it will be appreciated that the pressure wing 76 and the suction wing 77 can be described as including above 92 with after
Face 93.93 faced as indicated, 92 front end (or along updrift side) for facing gas turbine before each, and behind each
The rear end (or along downstream direction) of gas turbine.As indicated, interface 85 may be formed at the circumference weight of the pressure wing 76 and the suction wing 77
Between overlapping field.In this is circumferentially overlapping, according to preferred embodiment, the pressure wing 76 is positioned at the front of the suction wing 77.As will be appreciated
Arrive, in such situation, pressure wing contact surface 86 is formed on 93 behind the pressure wing 76, and sucks the shape of wing contact surface 87
Into before the suction wing 77 on 92.
According to some preferred embodiments, as shown in figures 13 and 14, pressure wing contact surface 86 can be configured to be attached to pressure
93 non-integration pad 91 behind the wing 76.In a similar manner, suction wing contact surface 87 is also configured to be attached to suck the wing 77
Above 92 non-integration pad 91.Non-integration pad 91 is attached to behind its pressure wing 76 93 and can be configured to generally flat surface.
Non-integration pad 91 is attached to before its suction wing 77 92 and is also configured to generally flat surface.In such situation, non-collection
The elevated contact surface on the wrapping surface attached by each non-integration pad therefore can be formed into pad 91.Think that other are constructed
It is possible, 93 non-integration pad 91 may include constant thickness behind the pressure wing 76 so that when its is attached to, and the pressure wing connects
Contacting surface 86 is shaped generally as flat surface.Similarly, 92 non-integration pad 91 may include constant thickness before the suction wing 77, make
Obtain when its is attached to, suction wing contact surface 87 is shaped generally as flat surface.
Additionally, as used for illustrative purposes herein, the lateral profile at interface 85 refers to such as from outer radial visual angle
The profile at the interface 85 of viewing.The example of the lateral profile at interface is depicted in Figure 13 and 14.Reference lateral profile (and it is specific
It is Figure 14), each in pressure wing contact surface 86 and suction wing contact surface 87 can be described as with distal edge 94 and proximal edge 95,
Distal edge 94 and proximal edge 95 are so named with a distance from the airfoil 25 attached by it on each.
Such as best illustrated in the lateral profile of Figure 14, pressure wing contact surface 86 and suction wing contact surface 87 may each comprise pass
In the oblique structure of flow direction 89.The oblique structure of pressure wing contact surface 86 may include in pressure wing contact surface 86 from distal edge
94 extend to the inclination toward or into direction of rotation 90 during proximal edge 95.On suction wing contact surface, oblique structure can be wrapped
Include and sucking the inclination toward or into direction of rotation 90 when wing contact surface 87 extends to distal edge 94 from proximal edge 95.Incline
Construction can be discussed in greater detail via the angle formed on flow direction 89.As indicated, the inclination of pressure wing contact surface 86 can
Form first jiao 96 between pressure wing contact surface 86 and flow direction 89, and between this first jiao 96 can spend 10 to 80,
Or between more preferably being spent 20 to 70.Similarly, the inclination of suction wing contact surface 87 can form suction wing contact surface 87 and flowing
Second jiao 97 between direction 89, and this second jiao 97 can 10 to 80 spend between, or more preferably 20 to 70 spend between.
As statement, predetermined migration of the invention may include one or more durection components, it compensates interface 85
In the contact surface 86,87 of between occur relative to deflection or movement.According to some preferred embodiments, such as Figure 14 middle fingers
Show, the predetermined migration at interface 85 includes circumferential component, and it will be referred to herein as circumferential offset 98.Circumferential offset 98 may include
Suction wing contact surface 87 is in front of the rotation of pressure wing contact surface 86.More specifically, on direction of rotation 90, predetermined migration can be wrapped
The distal edge 94 of suction wing contact surface 87 is included with circumferential offset 98 in front of the rotation of proximal edge 95 of pressure wing contact surface 86.It is predetermined
Skew may also include distal edge 94 of the proximal edge 95 of suction wing contact surface 87 with circumferential offset 98 in pressure wing contact surface 86 and revolve
Turn front.As it will be realized, the relative movement between pressure wing contact surface 86 and suction wing contact surface 87 is in airfoil 25
Solution pili torti may include estimated circumferential deflection when giving birth to, and circumferential offset 98 may be configured to corresponding to the deflection so that：The suction wing connects
The distal edge 94 of contacting surface 87 when expected operating condition closes gap 88, with the proximal edge 95 of pressure wing contact surface 86 circumferentially
Alignment；And the proximal edge 95 of wing contact surface 87 is sucked when expected operating condition closes gap 88, with pressure wing contact surface
86 distal edge 94 is circumferentially aligned.
According to other preferred embodiments, as shown in Figure 15, the predetermined migration at interface 85 includes radial component, and it will be at this
Referred to herein as radial deflection 99.More specifically, as indicated, radial deflection 99 may include pressure wing contact surface 86 on suction
Wing contact surface 87 offsets along outer radial or lateral direction.In such cases, as indicated, the outer ledge of pressure wing contact surface 86
101 can be positioned at outside by the radial deflection 99 of the outer ledge 101 of suction wing contact surface 87.Also as indicated, the pressure wing connects
The inside edge 102 of contacting surface 86 can be positioned at outside by the radial deflection 99 of the inside edge 102 of suction wing contact surface 87.Such as will
Recognize, the relative movement between pressure wing contact surface 86 and suction wing contact surface 87 is solved in airfoil due to service load
During torsion, estimated radial deflection, and the distance of radial deflection 99 can be caused to may be configured to correspond to the radial deflection so that：Pressure
The outer ledge 101 of power wing contact surface 86 when expected operating condition closes gap 88, the outside with suction wing contact surface 87
Edge 101 is radially aligned；And the inside edge 102 of pressure wing contact surface 86 closes gap 88 in expected operating condition
When, the inside edge 102 with suction wing contact surface 87 is radially aligned.
According to other preferred embodiments, the predetermined migration at interface 85 may include angular variation.Discussed as previously discussed with respect to Figure 14,
Each in contact surface 86,87 forms angle 96,97 on flow direction 89.Predetermined migration may include angular variation, and it is expressed as pressure
Difference between the angle 96,97 that power wing contact surface 86 and suction wing contact surface 87 and flow direction 89 are formed.As it will be realized,
Relative movement between pressure wing contact surface 86 and suction wing contact surface 87 can be led when airfoil solves torsion due to service load
Cause estimated angular deflection.According to preferred embodiment, the angular variation of predetermined migration may be configured to correspond to the angular deflection so that the pressure wing
Contact surface 86 is angulately aligned when operating condition closes gap 88 with suction wing contact surface 87.As it will be realized, working as this
When class angular alignment occurs, two angles 96,97 will be identical, i.e. pressure wing contact surface 86 will be parallel with suction wing contact surface 87.
Above-mentioned construction including predetermined migration can be used to improve the alignment of the contact position between the contact surface in interface, and
Thus the robustness of the contact for producing therebetween is improved.The alignment of the contact surface at contact point cause each contact surface completely relative to
Mutual compression.Complete compressive state obtained by this can be used to limit or eliminate the generation of the stretching and shear stress being more harmful to,
They are the stress risers for making component degenerate quickly, particularly when wear pad is the non-integration component of rotor blade.As will be appreciated
Arrive, this is an advantage over being placed in such non-integration wear pad in being formed in and is set across the tradition in the recess in the surface of the wing of shield
The improvement of meter.Such conventional arrangement increases the caused tensile force in wear pad, and thereby increase wear pad tear and
Liberticidal possibility.This causes by wear pad the wind of the non-programmed halt for causing is ftractureed or ruptured due to contact load high
Danger raises.By contrast, construction of the invention can be used under the conditions of such contact load high, without shortening component's life or increasing
Plus the risk of such failure.
Referring now to Figure 16 and 17, alternative of the invention is shown, it can be used in increase across the boundary of shield 75
Face 85 keeps the possibility of the favourable alignment of air force during operation.As it will be realized, the pressure wing 76 at interface 85 with
The scope of relative movement and the movement between the suction wing 77 may include wherein period of the anticipated movement different from actual conditions.Example
Such as, this can be so in the transient for operating period or during being related to anomalous event such as component failures or the irregular operation of system.
Give everything, turbine operator preferably have in across hood structure, its prevention pressure wing 76 and the suction wing 77 are with negatively
Influence the possibility of the mode misalignment of aerodynamic quality.In such cases, alternative aspect of the invention and such as figure
Shown in 16 and 17, the prevention can be configured so that they cooperatively form particular configuration by by the pressure wing 76 and the suction wing 77
To realize, the particular configuration will be referred to herein as the ladder 110 that downstream narrows.
It is of the invention downstream narrow ladder 110 can by make the wing 76,77 of shield be configured with different radial thickness and
Then by them on mutually positioning, so that the radial thickness of component reduces along downstream or rear direction, even and if causing the wing
The aligned in general is also kept to construct under the operating condition of 76,77 quite big radial deflection.The more discussions of following article, this can
By producing radial direction buffer part to realize, the radial direction buffer part is allowed in the wing 76, the forward position of the misalignment generation between 77 either one
To significantly relatively radially moving for (that is, inner or outer side).In this manner, interface 85 may be configured to, and increase is most preceding or (such as it will
Be generally known as herein) before the bigger air force of " the upstream wing " 92 to the possibility in working fluid stream, without
By the wing 76, what the relatively radially movement between 77 is originally, though unforeseen situation or it is abnormal cause it is unexpected or
In the relative movement being expected outside standard.Therefore, according to exemplary embodiment, the interface with the ladder 110 for downstream narrowing
85 may include the most preceding or upstream wing 76,77 (it can be the pressure wing 76 according to some preferred embodiments, but be alternatively the suction wing 77),
It is configured so as to have than the downstream wing 76,77 bigger radial thickness, and the downstream wing is to will be used herein to represent most rear wing
Term.According to preferred embodiment, between the radial thickness of the upstream wing can be for 1.05 to 1.5 times of the radial thickness of the downstream wing,
Or more preferably between 1.2 to 1.4 times.
For the description purpose on Figure 16 and 17, term " radial extension " refers to be limited to the pressure wing 76 or the suction wing 77
Outer ledge 111 and inside edge 112 between scope.The scope can be regarded as being limited by the rotor blade in mounting condition
It is fixed, and it will thus be appreciated that radial extension in working-fluid flow path.Additionally, the radial extension of rotor blade can be cold
Determine in structural regime.Therefore it is presumed that in this construction, the pressure wing 76 is the upstream wing and sucks the wing 77 for the downstream wing, this hair
Bright embodiment includes the pressure wing 76 and the suction wing 77, and they are radially located into so that in the area for circumferentially overlapping at interface 85
In section, the radial extension for sucking the wing 77 is less than the radial extension of the pressure wing 76 and is completely contained in the radial extension of the pressure wing 76
It is interior.Give the construction, it will be appreciated that the pressure wing 76 and the suction wing 77 are configured so that the outer ledge 111 of the pressure wing 76
The outside of the outer ledge 111 of the suction wing 77 is resided in, as shown.Such as further instruction, the outer ledge 111 of the pressure wing 76
Buffer part is may make up along the radial direction difference that lateral direction offsets from the outer ledge 111 of the suction wing 77, it will be referred to herein as
Outside buffer part 113.The pressure wing 76 and the suction wing 77 can be further constructed so that the inside edge 112 of the pressure wing 76 resides in
Suck the inner side of the inside edge 112 of the wing 77.As indicated, the inside edge 112 of the pressure wing 76 from suction the wing 77 inside edge
The 112 radial direction differences offset along inner side direction may make up buffer part, and it will be referred to herein as inner side buffer part 114.To such as recognize
Know, the category of outside buffer part 113 and inner side buffer part 114 is configured to provide the possibility of following increase：Group
In relative movement between the pressure wing 76 and the suction wing 77 of the part in large range of possible operating condition and on it, keep
The favourable ladder 110 that downstream narrows of air force.
As it will be realized, the continuation holding of downstream narrow ladder 110 through large range of operating condition can be big
Overall air power performance is improved on body.This by realize interface 85 the upstream wing 76,77 smooth fixed wheel exterior feature before 92 replace
For the downstream wing 76,92 congregation working fluid streams are completed before 77, the downstream wing 76, and before 77 92 because it is used as contact surface
Expected major function and be typically configured as blunt, flat, smaller aerofoil.I other words, as indicated, the upstream wing 76,
92 are typically configured as smooth air force conical surface before 77, and it is tapered along updrift side or narrows, because meaning
Figure is that it directly interacts with working fluid stream.The downstream wing 76,92 are often constructed to blunt plane before 77, its
Directly it is targeted in working fluid stream, because being not intended to be performed on aerodynamic purpose, but as contact surface.
Preferably, according to the present invention, the dull face is maintained in the tail (wake) of the upstream wing wider 76,77 or by the upstream wing wider
76,77 protection, so that it is indirect and limited with the interaction of working fluid.Otherwise, it will negatively affect air and move
Power performance.As it will be realized, avoiding such aerodynamic losses from can generally improving the overall efficiency of engine.
As the skilled person will recognize, above for many different characteristics of some exemplary embodiments description
Further optionally can apply to form other possible embodiments of the invention with construction.For simplicity and consider
To the ability of those skilled in the art, all possible repetition is not provided or is discussed in detail, but following some embodiments or
All combinations that further embodiment is included and possible embodiment are it is intended that the part of the application.Additionally, people in the art
Member will discover improvement, change and retrofits from the above description of some exemplary embodiments of the invention.In the technology of this area
Such improvements, changes and modifications are also intended to be covered by the appended claims.In addition, it will be apparent that, this is only related to above
The embodiment of the description of application, and can many changes may be made herein and remodeling, without deviating from such as by following claims
The spirit and scope limited with its equivalent.
Claims (10)
1. a kind of rotor blade for gas turbine, the rotor blade configuration be used for attach to rotor disk and around
Used in the rotor blade of the circumferentially spaced row's same configuration of rotor disk, the rotor blade also includes：
Airfoil, it is limited between shaped pressure face and laterally relative convex suction plane, wherein the pressure face and institute
State suction plane to be axially extended between relative leading edge and trailing edge, and radially prolong between outside end and medial extremity
Stretch, the medial extremity attaches to the root for being configured to that the rotor blade is attached to the rotor disk；And
In across shield, it includes the pressure wing extended from the pressure face of the airfoil and the suction from the airfoil
Enter the suction wing of face extension；
The pressure wing and the suction wing in wherein described across shield are configured so as to cooperatively form a row identical
Interface between the adjacent rotor blades of the installation in the rotor blade in the rotor blade of construction；
Wherein described interface includes：
The pressure wing contact surface on the pressure wing is arranged on, it connects across gap with the suction wing being arranged on the suction wing
Contacting surface is relative；And
Predetermined migration between the pressure wing contact surface and the suction wing contact surface, the predetermined migration is configured to pre-
When phase operating condition makes the gap-closing so that producing contact therebetween, make the pressure wing contact surface relative to the suction
Wing contact surface is desirably aligned.
2. rotor blade according to claim 1, it is characterised in that the airfoil includes torsion formation, wherein described
Airfoil configuration into when the airfoil is radially extended between the medial extremity and the outside end, with around vertical
The torsion of axis, its solution turns round the relative shifting caused between the pressure wing contact surface at the interface and the suction wing contact surface
It is dynamic；
Wherein described expected operating condition includes causing the torsion formation of the airfoil fully to solve torsion to make the gap
The operating condition of closure；And
Wherein described expected operating condition includes the desired speed of the rotor blade in the turbine.
3. rotor blade according to claim 2, it is characterised in that the desired speed includes corresponding to the combustion gas
The rotating speed of the operation at the 90% of the nominal load of turbine or higher than 90%；
The torsion formation of wherein described airfoil is configured so as to little by little change between the medial extremity and outside end
Become the alternate angle for the airfoil；And
Include across shield the shield in the position range that is arranged on the airfoil in wherein described, the position range is limited
It is outer at inboard boundary and the 85% of the radial height of the airfoil at the 25% of the radial height of the airfoil
Between lateral boundaries.
4. rotor blade according to claim 1, it is characterised in that the gas turbine is included limiting through being positioned at
Compressor at front end and be positioned at rear end turbine working-fluid flow path, its orientation limited in described gas turbine
Front direction and rear direction；
Wherein flow direction includes working fluid through the expected flow direction in the working-fluid flow path, the flowing side
To the central axis for being defined as parallel in the compressor and the turbine gas turbine, and along the rear direction
Orientation；And
Wherein direction of rotation includes the expected direction of rotation for the rotor blade during the operation of the gas turbine.
5. rotor blade according to claim 4, it is characterised in that the rotor blade includes being configured to described
The rotor blade used in turbine；
Wherein described interface is formed between the section for circumferentially overlapping of the pressure wing and the suction wing；And
Wherein：
The pressure wing includes front and back, described above to face the front end of the gas turbine, and it is described behind
Face the rear end of the gas turbine；And
The suction wing includes front and back, described above to face the front end of the gas turbine, and it is described behind
Face the rear end of the gas turbine.
6. rotor blade according to claim 5, it is characterised in that described in the pressure wing and the suction wing
In the section for circumferentially overlapping, the pressure wing is positioned at the suction wing front so that：
The pressure wing contact surface be formed in the pressure wing it is described below on；And
It is described suction wing contact surface be formed in it is described suction the wing it is described above on.
7. rotor blade according to claim 6, it is characterised in that：
The pad of the pressure wing contact surface including non-integration, its be attached to the pressure wing it is described behind flat section and from
Its protrusion；And
The suction wing contact surface includes the pad of non-integration, its be attached to the suction wing it is described before flat section and from
Its protrusion.
8. gas turbine according to claim 7, it is characterised in that：
The pressure wing it is described behind the pad of the non-integration include the thickness of constant so that be attached to the pressure
The power wing it is described behind the flat section when, the pressure wing contact surface is flat；
The suction wing it is described before the pad of the non-integration include the thickness of constant so that be attached to the suction
Enter the wing it is described before the flat section when, the suction wing contact surface is flat；And
Each in the pad of wherein described non-integration includes high-abrasive material.
9. gas turbine according to claim 7, it is characterised in that lateral profile is included as watched from outer radial visual angle
The profile at the interface；And
Wherein press the lateral profile：
On with a distance from the airfoil, the pressure wing contact surface includes distal edge and proximal edge；And
On with a distance from the airfoil, the suction wing contact surface includes distal edge and proximal edge.
10. gas turbine according to claim 9, it is characterised in that by the lateral profile, the pressure wing contact surface
Include the oblique structure on the flow direction with the suction wing contact surface；And
Wherein：
The oblique structure of the pressure wing contact surface is included in the pressure wing contact surface and extends to institute from the distal edge
Towards the inclination of the direction of rotation of the rotor blade when stating proximal edge；And
The oblique structure of the suction wing contact surface is included in the suction wing contact surface and extends to institute from the proximal edge
Towards the inclination of the direction of rotation of the rotor blade when stating distal edge.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US14/979,812 US10221699B2 (en) | 2015-12-28 | 2015-12-28 | Shrouded turbine rotor blades |
| US14/979812 | 2015-12-28 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106917643A true CN106917643A (en) | 2017-07-04 |
| CN106917643B CN106917643B (en) | 2021-04-20 |
Family
ID=57570734
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611235488.1A Active CN106917643B (en) | 2015-12-28 | 2016-12-28 | Shrouded turbine rotor blade |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US10221699B2 (en) |
| EP (1) | EP3187689B1 (en) |
| JP (1) | JP6866145B2 (en) |
| CN (1) | CN106917643B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110374685A (en) * | 2019-07-17 | 2019-10-25 | 中国航发沈阳发动机研究所 | Sawtooth is preced with rotor blade non-working surface sideshake control method and aero-engine |
| CN114233399A (en) * | 2022-02-23 | 2022-03-25 | 成都中科翼能科技有限公司 | Method for controlling contact stress of turbine rotor blade shroud contact surface |
| CN114320480A (en) * | 2020-09-30 | 2022-04-12 | 通用电气公司 | Rotor blade damping structure |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10287895B2 (en) | 2015-12-28 | 2019-05-14 | General Electric Company | Midspan shrouded turbine rotor blades |
| US10196908B2 (en) * | 2016-02-09 | 2019-02-05 | General Electric Company | Turbine bucket having part-span connector and profile |
| US10001014B2 (en) | 2016-02-09 | 2018-06-19 | General Electric Company | Turbine bucket profile |
| US10190421B2 (en) | 2016-02-09 | 2019-01-29 | General Electric Company | Turbine bucket having tip shroud fillet, tip shroud cross-drilled apertures and profile |
| US10125623B2 (en) | 2016-02-09 | 2018-11-13 | General Electric Company | Turbine nozzle profile |
| US10156149B2 (en) | 2016-02-09 | 2018-12-18 | General Electric Company | Turbine nozzle having fillet, pinbank, throat region and profile |
| US10221710B2 (en) | 2016-02-09 | 2019-03-05 | General Electric Company | Turbine nozzle having non-axisymmetric endwall contour (EWC) and profile |
| US10161255B2 (en) | 2016-02-09 | 2018-12-25 | General Electric Company | Turbine nozzle having non-axisymmetric endwall contour (EWC) |
| US10190417B2 (en) | 2016-02-09 | 2019-01-29 | General Electric Company | Turbine bucket having non-axisymmetric endwall contour and profile |
| US11739645B2 (en) | 2020-09-30 | 2023-08-29 | General Electric Company | Vibrational dampening elements |
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| US10287895B2 (en) | 2015-12-28 | 2019-05-14 | General Electric Company | Midspan shrouded turbine rotor blades |
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- 2016-12-15 JP JP2016242824A patent/JP6866145B2/en active Active
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| US4257741A (en) * | 1978-11-02 | 1981-03-24 | General Electric Company | Turbine engine blade with airfoil projection |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110374685A (en) * | 2019-07-17 | 2019-10-25 | 中国航发沈阳发动机研究所 | Sawtooth is preced with rotor blade non-working surface sideshake control method and aero-engine |
| CN114320480A (en) * | 2020-09-30 | 2022-04-12 | 通用电气公司 | Rotor blade damping structure |
| CN114233399A (en) * | 2022-02-23 | 2022-03-25 | 成都中科翼能科技有限公司 | Method for controlling contact stress of turbine rotor blade shroud contact surface |
| CN114233399B (en) * | 2022-02-23 | 2022-05-17 | 成都中科翼能科技有限公司 | Method for controlling contact stress of turbine rotor blade shroud contact surface |
Also Published As
| Publication number | Publication date |
|---|---|
| US10221699B2 (en) | 2019-03-05 |
| JP6866145B2 (en) | 2021-04-28 |
| EP3187689A1 (en) | 2017-07-05 |
| JP2017122444A (en) | 2017-07-13 |
| EP3187689B1 (en) | 2019-06-05 |
| US20170183973A1 (en) | 2017-06-29 |
| CN106917643B (en) | 2021-04-20 |
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Effective date of registration: 20240102 Address after: Swiss Baden Patentee after: GENERAL ELECTRIC CO. LTD. Address before: New York State, USA Patentee before: General Electric Co. |